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Transient liquid phase infiltration repair method for large gap defects in superalloy hot end parts

A technology for hot-end parts and superalloys, which is applied in the field of transient liquid phase infiltration repair of large gap defects in superalloy hot-end parts, can solve problems such as low strength, inability to be repaired reliably in time, and difficult to repair, and achieve extended service life, Achieving the effect of simultaneous processing of large batches and saving operating costs

Active Publication Date: 2016-01-13
INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a method for repairing large-gap defect transient liquid phase infiltration of superalloy hot-end parts to solve cracks and ablation holes in nickel-based, cobalt-based and iron-based superalloy hot-end parts with high Al and Ti content , Corrosion pits and wear and other large gap defects are difficult to repair, low strength, and cannot be repaired in a timely and reliable manner

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0048] There are three thermal fatigue cracks on the edge plate of the three-piece guide vane of an aero-engine, the crack length is about 20mm, and the depth is penetrating. The crack is at the corner between the edge plate and the blade body, where the wall thickness is about 3mm. The blade is a hollow structure, and the material of the blade is K417G alloy. The total content of Al+Ti in the alloy is more than 9wt%, so it is difficult to repair by argon arc welding. The invention can not only heal the cracks quickly and conveniently, but also meet the service performance requirements of the blades.

[0049] The repair process of the thermal crack of the three-piece guide vane:

[0050] Use mechanical grinding to remove thermal cracks → clean with acetone → plasticize the filling material and fill it into the three-dimensional space gap formed by grinding → high temperature sintering → mechanical grinding and shaping → plasticize the nickel-based brazing material and place i...

Embodiment 2

[0061] The tip of a heavy-duty gas turbine blade is worn after long-term service, and the wear amount is about 5mm. The blade is a hollow structure, and the blade material is K438G alloy. The total content of Al+Ti in the alloy is more than 7wt%, so it is difficult to repair by argon arc welding. If high-energy micro-arc spark deposition and pulse laser welding are used to repair, the workload is large and the efficiency is low. Adopting the invention can not only quickly and conveniently lengthen the blade tip wear, but also can carry out batch processing, which can greatly improve the efficiency and reduce the repair cost.

[0062] Repair process for blade tip wear and extension:

[0063] Use mechanical grinding to remove thermal cracks → clean with acetone → plasticize the filling material and place it on the tip of the blade → high temperature sintering → mechanical grinding and shaping → plasticize the nickel-based brazing material and place it on the tip of the blade → s...

Embodiment 3

[0074] During maintenance of an imported gas turbine, severe corrosion and multiple penetrating cracks were found in the nozzle of the gas turbine. The material of the nozzle is FSX-414 cobalt-based alloy, and the exhaust edge of the nozzle is formed by hot corrosion with large corrosion pits. If laser welding is used, complex molds and three-axis linkage machine tools are required to match it. The modification process is complicated, the workload is too large, and the efficiency is low. By adopting the invention, all the cracks and the lack of geometric dimensions such as corrosion pits can be repaired together, and the efficiency is high and the quality is good. The repair process of FSX-414 alloy nozzle is:

[0075] Organic solvent (acetone) degreasing treatment→mechanically remove the oxidized corrosion layer on the crack surface and corrosion pit surface→clean with acetone→coat the plasticized cobalt-based alloy on the crack and corrosion pit space→heat for porous sinter...

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Abstract

The invention relates to the field of high temperature alloy hot end part repairing, in particular to a high temperature alloy hot end part large gap defect transient state liquid phase infiltration repairing method. The method includes (1) removing an oxide layer and the like on the surface of a defect of a high temperature alloy hot end part to enable the defect position to have metal luster; (2) adopting nickel-base or cobalt-base alloy powder to fill the defect space, conducting molding in a plasticizing mode and then conducting high temperature sintering; (3) arranging the nickel-base alloy powder subjected to B Zr or Hf activating treatment above filling metal, conducting high temperature transient state liquid phase infiltration to achieve compacting; (4) conducting polishing and clearing; (5) conducting homogenizing treatment on the high temperature alloy hot end part under high temperature. The method can solve the problem that Al+Ti high temperature alloy hot end part is low in large gap defect repairing strength and easy to scrape, achieves high strength connection, is high in repairing yield and can overcome large gap defects such as crack, ablation holes and corrosion pits of hot end parts of aero engines, electric gas turbines, naval vessel gas turbines and caused in a service use process.

Description

Technical field: [0001] The invention relates to the field of repairing high-temperature alloy hot-end parts, in particular to a method for repairing large-gap defects of high-temperature alloy hot-end parts by transient liquid phase infiltration. Background technique: [0002] The hot-end components such as turbine blades, guide vanes, and nozzles of aero-engines and industrial gas turbines are prone to large gap defects such as cracks, ablation holes, corrosion pits, and wear during long-term service. As the output power of aeroengines and industrial gas turbines increases, the wear, corrosion, and ablation damage of hot-end components become more and more serious. [0003] Aeroengines and industrial gas turbine hot end parts are usually made of nickel-based and cobalt-based alloys with excellent high-temperature mechanical properties, high-temperature oxidation resistance, and corrosion resistance, and are designed with complex profiles and cooling structures. These part...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23P6/00
CPCB23P6/045
Inventor 谢玉江杨彦红王明生韩旭
Owner INST OF METAL RESEARCH - CHINESE ACAD OF SCI
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